Results
2014-23-07: We are superseding Airworthiness Directive (AD) 2004-16-01 for certain Airbus Model A330-200 and -300 series airplanes and Model A340- 200 and -300 series airplanes. AD 2004-16-01 required repetitive inspections for cracking of the chromed area of the left and right piston rods for the main landing gear (MLG) retraction actuators, and related investigative and corrective actions if necessary. This new AD requires repetitive draining of any fluid from the retraction actuator piston rod internal volume and sealing of the vent hole; repetitive ultrasonic inspections of the upper end of the piston rods, and corrective actions if necessary; a one-time ultrasonic inspection (longitudinal and circumferential) of the full length of the piston rod, and corrective actions if necessary; and a terminating modification of the left-hand and right-hand MLG retraction actuators. This AD was prompted by reports of the piston rods for the MLG retraction actuators rupturing during flight. We areissuing this AD to prevent cracking of the piston rods for the MLG retraction actuators, which could result in rupture of a piston rod, non-damped extension of the MLG, high loads on the fully extended MLG, and consequent reduced structural integrity of the MLG.
92-09-01: 92-09-01 AEROSPATIALE: Amendment 39-8226. Docket No. 92-NM-66-AD. Applicability: Model ATR42-200 and -300 series airplanes, as listed in Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; and Model ATR72-100 and -200 series airplanes, as listed in Aerospatiale Service Bulletin ATR72-76-1002, Revision 1, dated December 5, 1991; certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless accomplished previously. To prevent the crew's inability to increase or decrease engine power, accomplish the following: (a) Install a heat deflector on the rear upper cowl, and a thermal bridge between the teleflex controls and the air conditioning duct, in accordance with Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; or Aerospatiale Service Bulletin ATR72- 76-1002, Revision 1, dated December 5, 1991; as applicable. (b) An alternative method of compliance oradjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installations shall be done in accordance with Aerospatiale Service Bulletin ATR42-76-0009, Revision 1, dated December 5, 1991; or Aerospatiale Service Bulletin ATR72- 76-1002, Revision 1, dated December 5, 1991; as applicable. These service bulletins include the following list of effective pages: Service Bulletin Page Revision Number Date 1-6, 8-12, 15-17 1 December 5, 1991 ATR42-76-0009, Revision 1 7, 13-14, 18 Original April 11, 1991 1-2, 6-10, 13-14 1 December 5, 1991 ATR72-76-1002 Revision 1 3-5, 11-12, 15-16 Original April 11, 1991 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on May 8, 1992.
2014-23-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 series airplanes, Model A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a circumferential crack at the gland retaining-ring groove of certain retraction actuators on the main landing gear (MLG). This AD requires an inspection to identify the part numbers of MLG retraction actuators and replacement of certain MLG retraction actuators. We are issuing this AD to prevent MLG retraction actuator failure that could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing or rollout, and consequent damage to the airplane and injury to the occupants.
2000-05-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive inspections to detect cracking of various areas of the forward pressure bulkhead, and repair, if necessary. This amendment also provides for certain optional preventive modifications, which, if accomplished, would terminate the repetitive inspections for the affected areas. This amendment is prompted by reports indicating that numerous fatigue cracks were found on critical areas of the forward pressure bulkhead. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in rapid decompression of the airplane fuselage.
2000-05-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracking on the door edge frames of the fuselage bulk cargo compartment, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracks in the door edge frames of the fuselage bulk cargo compartment, which could result in reduced structural integrity of the airframe.
2021-17-06: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, -100B, -100B SUD, -200B, -200C, - 200F, -300, -400, -400D, -400F, 747SR, and 747SP airplanes. This AD was prompted by reports of cracks found in the front spar shear tie and at the intercostal lug fitting at certain locations. This AD requires repetitive detailed and surface high frequency eddy current (HFEC) inspections of the front spar shear tie and intercostal lug fitting at certain locations for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-23-02: We are adopting a new airworthiness directive (AD) for certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD requires repetitively performing a magnetic particle inspection of the Gleason crown for a crack. This AD was prompted by a report of a crack that was found on a Gleason crown, which if not detected, could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.
2000-05-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires a one-time inspection of the main landing gear (MLG) axle flange to detect cracking, and follow- on corrective actions. For certain airplanes, this amendment also requires replacement of the original brake mounting gasket with a more durable aluminum-nickel-bronze gasket, and installation of new shear studs, if necessary. For certain airplanes, this amendment requires modification of the mounting flange holes of the brake torque tube. This amendment is prompted by reports of cracking in the axle flange and by reports of deterioration of the brake mounting gasket. The actions specified by this AD are intended to prevent fracture of the MLG axle and separation of the wheel from the MLG, and consequent reduced controllability of the airplane.
91-11-07: 91-11-07 FOKKER: Amendment 39-7003. Docket No. 90-NM-291-AD. Applicability: Model F-28 series airplanes, Serial Numbers 11003 through 11013, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Within one year after the effective date of this AD, remove the cold-bonded lap joint rivets, and perform detailed visual and high frequency eddy current inspections to detect cracks and damage to the areas adjacent to the rivet holds, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/53-109, dated October 24, 1990. 1. If no cracks or damage are found, prior to further flight, install 3/16-inch protruding-head rivets in accordance with the Accomplishment Instructions of the service bulletin. 2. If cracks or damage are found, prior to further flight, repair and install 3/16-inch protruding-head rivets in accordance with the Accomplishment Instructions of the service bulletin. B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest MountainRegion, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7003, AD 91-11-07) becomes effective on June 24, 1991.
88-20-08: 88-20-08 HAMILTON STANDARD: Amendment 39-6009. Applies to Hamilton Standard Model 14SF-5 and 14SF-7 propellers equipped with plastic "Rynite" retaining rings, P/N 785540, installed on, but not limited to, Dehavilland Dash 8 and Aerospatiale/ Aeritalia ATR-42 aircraft. Compliance is required as indicated, unless already accomplished. To prevent loss of the plastic "Rynite" blade retaining rings, P/N 785540, and severe damage to the blade retention system with resultant propeller unbalance, accomplish the following: (a) Within the next 50 hours time in service after May 21, 1987, and thereafter at intervals not to exceed 200 hours time in service, until accomplishment of paragraph (c), inspect the plastic "Rynite" blade retaining rings, P/N 785540, on all four blades in accordance with Hamilton Standard Alert Service Bulletin (ASB) 14SF-61-A21, Revision 2, dated March 27, 1987. (b) If any evidence of cracks is discovered as a result of an inspection required by paragraph (a), prior to further flight remove from service both halves of blade retaining rings and replace with new or serviceable retaining ring halves in accordance with Hamilton Standard ASB 14SF-61-A21, Revision 2, dated March 27, 1987, or accomplish paragraph (c) below prior to further flight. (c) Replace, not later than July 31, 1989, the plastic "Rynite" blade retaining rings, P/N 785540, with aluminum blade retaining rings, P/N 794345, on all four blades in accordance with Hamilton Standard Service Bulletin 14SF-61-17, Revision 1, dated October 1, 1987. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, may adjust the compliance time specified in this AD. Hamilton Standard ASB 14SF-61-A21, Revision 2, dated March 27, 1987, and ASB 14SF-61-17, Revision 1, dated October 1, 1987, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Hamilton Standard Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Docket 87-ANE-13, between the hours of 8:00 a.m.and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-6009, supersedes AD 87-10-05, Amendment 39-5609. This amendment, 39-6009, becomes effective on October 31, 1988.